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NO20051543L - Rotor blade with rod-shaped damper - Google Patents

Rotor blade with rod-shaped damper

Info

Publication number
NO20051543L
NO20051543L NO20051543A NO20051543A NO20051543L NO 20051543 L NO20051543 L NO 20051543L NO 20051543 A NO20051543 A NO 20051543A NO 20051543 A NO20051543 A NO 20051543A NO 20051543 L NO20051543 L NO 20051543L
Authority
NO
Norway
Prior art keywords
foot
tip
rotor blade
edge surface
rod
Prior art date
Application number
NO20051543A
Other languages
Norwegian (no)
Other versions
NO20051543D0 (en
Inventor
Raymond Surace
Tracy Propheter
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of NO20051543D0 publication Critical patent/NO20051543D0/en
Publication of NO20051543L publication Critical patent/NO20051543L/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Fluid-Damping Devices (AREA)
  • Multiple-Way Valves (AREA)
  • Rotary Pumps (AREA)

Abstract

En rotorbladdemper (48) inkluderer et legeme (58) med en fot (60), en tupp (62), en første kontaktflate (69), en andre kontaktflate (66), en følgende kantflate (68) og en førende kantflate (70). De følgende og førende kantflater (68, 70) strekker seg mellom kontaktflatene (64, 66). Den første kontaktflaten (64), andre kontaktflate (66), den følgende kantflate (68) og den førende kantflate (70) strekker seg alle lengdemessig mellom fot (60) og tupp (62). Legemet (58) omfatter minst én kjøleåpning (82) plassert nær foten (60), som har en diameter som er omtrent lik eller større enn bredden av den følgende kantflate (68) nær tuppen (62). Legemet (58) avsmalner mellom fot (60) og tupp (62) slik at et første tverrsnittsområde nær foten (60) er større enn et andre tverrsnittsområde nær tuppen (62).A rotor blade damper (48) includes a body (58) with a foot (60), a tip (62), a first contact surface (69), a second contact surface (66), a subsequent edge surface (68) and a leading edge surface (70). ). The following and leading edge surfaces (68, 70) extend between the contact surfaces (64, 66). The first contact surface (64), second contact surface (66), the following edge surface (68) and the leading edge surface (70) all extend longitudinally between the foot (60) and the tip (62). The body (58) comprises at least one cooling opening (82) located near the foot (60), having a diameter approximately equal to or greater than the width of the following edge surface (68) near the tip (62). The body (58) tapered between the foot (60) and the tip (62) so that a first cross-sectional area near the foot (60) is larger than a second cross-sectional area near the tip (62).

NO20051543A 2004-05-27 2005-03-23 Rotor blade with rod-shaped damper NO20051543L (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/855,184 US7217093B2 (en) 2004-05-27 2004-05-27 Rotor blade with a stick damper

Publications (2)

Publication Number Publication Date
NO20051543D0 NO20051543D0 (en) 2005-03-23
NO20051543L true NO20051543L (en) 2005-11-28

Family

ID=34940667

Family Applications (1)

Application Number Title Priority Date Filing Date
NO20051543A NO20051543L (en) 2004-05-27 2005-03-23 Rotor blade with rod-shaped damper

Country Status (12)

Country Link
US (1) US7217093B2 (en)
EP (1) EP1602801B1 (en)
JP (1) JP2005337237A (en)
KR (1) KR20060044732A (en)
AT (1) ATE362036T1 (en)
AU (1) AU2005201263A1 (en)
CA (1) CA2501160A1 (en)
DE (1) DE602005001085T2 (en)
NO (1) NO20051543L (en)
PL (1) PL1602801T3 (en)
SG (1) SG117530A1 (en)
TW (1) TW200538625A (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7625178B2 (en) * 2006-08-30 2009-12-01 Honeywell International Inc. High effectiveness cooled turbine blade
US7736124B2 (en) * 2007-04-10 2010-06-15 General Electric Company Damper configured turbine blade
US8579593B2 (en) * 2009-11-06 2013-11-12 Siemens Energy, Inc. Damping element for reducing the vibration of an airfoil
JP5660883B2 (en) 2010-12-22 2015-01-28 三菱日立パワーシステムズ株式会社 Steam turbine vane, steam turbine
US9403208B2 (en) 2010-12-30 2016-08-02 United Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
US9175570B2 (en) 2012-04-24 2015-11-03 United Technologies Corporation Airfoil including member connected by articulated joint
US9133712B2 (en) 2012-04-24 2015-09-15 United Technologies Corporation Blade having porous, abradable element
US9181806B2 (en) 2012-04-24 2015-11-10 United Technologies Corporation Airfoil with powder damper
US8915718B2 (en) 2012-04-24 2014-12-23 United Technologies Corporation Airfoil including damper member
US9296039B2 (en) 2012-04-24 2016-03-29 United Technologies Corporation Gas turbine engine airfoil impingement cooling
US9074482B2 (en) 2012-04-24 2015-07-07 United Technologies Corporation Airfoil support method and apparatus
US9404369B2 (en) 2012-04-24 2016-08-02 United Technologies Corporation Airfoil having minimum distance ribs
US9243502B2 (en) 2012-04-24 2016-01-26 United Technologies Corporation Airfoil cooling enhancement and method of making the same
US9249668B2 (en) 2012-04-24 2016-02-02 United Technologies Corporation Airfoil with break-way, free-floating damper member
US9267380B2 (en) 2012-04-24 2016-02-23 United Technologies Corporation Airfoil including loose damper
US9470095B2 (en) 2012-04-24 2016-10-18 United Technologies Corporation Airfoil having internal lattice network
US9121288B2 (en) 2012-05-04 2015-09-01 Siemens Energy, Inc. Turbine blade with tuned damping structure
WO2015112891A1 (en) * 2014-01-24 2015-07-30 United Technologies Corporation Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade
JP5805283B2 (en) * 2014-09-10 2015-11-04 三菱日立パワーシステムズ株式会社 Steam turbine vane, steam turbine
JP5766861B2 (en) * 2014-09-10 2015-08-19 三菱日立パワーシステムズ株式会社 Steam turbine vane, steam turbine
US10774653B2 (en) 2018-12-11 2020-09-15 Raytheon Technologies Corporation Composite gas turbine engine component with lattice structure
US11371358B2 (en) 2020-02-19 2022-06-28 General Electric Company Turbine damper
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements
US11808166B1 (en) * 2021-08-19 2023-11-07 United States Of America As Represented By The Administrator Of Nasa Additively manufactured bladed-disk having blades with integral tuned mass absorbers

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB347964A (en) 1929-07-05 1931-05-07 British Thomson Houston Co Ltd Improvements in and relating to vibration damping devices particularly for turbines, propellers and the like
US2689107A (en) * 1949-08-13 1954-09-14 United Aircraft Corp Vibration damper for blades and vanes
GB2097479B (en) * 1981-04-24 1984-09-05 Rolls Royce Cooled vane for a gas turbine engine
US5407321A (en) * 1993-11-29 1995-04-18 United Technologies Corporation Damping means for hollow stator vane airfoils
US5820343A (en) * 1995-07-31 1998-10-13 United Technologies Corporation Airfoil vibration damping device
US5558497A (en) * 1995-07-31 1996-09-24 United Technologies Corporation Airfoil vibration damping device
GB9906450D0 (en) * 1999-03-19 1999-05-12 Rolls Royce Plc Aerofoil blade damper
US6929451B2 (en) * 2003-12-19 2005-08-16 United Technologies Corporation Cooled rotor blade with vibration damping device

Also Published As

Publication number Publication date
PL1602801T3 (en) 2007-09-28
TW200538625A (en) 2005-12-01
JP2005337237A (en) 2005-12-08
AU2005201263A1 (en) 2005-12-15
US20050265843A1 (en) 2005-12-01
KR20060044732A (en) 2006-05-16
EP1602801A1 (en) 2005-12-07
DE602005001085D1 (en) 2007-06-21
DE602005001085T2 (en) 2007-11-22
NO20051543D0 (en) 2005-03-23
EP1602801B1 (en) 2007-05-09
CA2501160A1 (en) 2005-11-27
US7217093B2 (en) 2007-05-15
SG117530A1 (en) 2005-12-29
ATE362036T1 (en) 2007-06-15

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